Low energy trajectories for the Moon-to-Earth space flight |
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Authors: | V V Ivashkin |
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Institution: | (1) Keldysh Institute of Applied Mathematics, Miusskaya Sq. 4, 125 047 Moscow, Russia |
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Abstract: | The Moon-to-Earth low energy trajectories of ‘detour’ type are found and studied within the frame of the Moon-Earth-Sun-particle
system. These trajectories use a passive flight to the Earth from an initial elliptic selenocentric orbit with a high aposelenium.
The Earth perturbation increases the particle selenocentric energy from a negative value first to zero and then to a positive
one and therefore leads to a passive escape of the particle motion from the Moon attraction near the translunar libration
pointL
2. This results in the particle flight to a distance of about 1.5 million km from the Earth where the Sun gravitation decreases
the particle orbit perigee distance to a small value that leads to the particle approaching the Earth vicinity in about 100
days of the flight. A set of the Moon-to-Earth ‘detour’ trajectories is defined numerically. Characteristics of these trajectories
are presented. The ‘detour’ trajectories give essential economy of energy (about 150 m/s in Delta V) relative to the usual
ones. |
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Keywords: | ‘ Detour’ lunar trajectories Moon-Earth flight escape gravitational perturbations |
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